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GB1112260A - A frangible high-altitude propulsion motor - Google Patents

A frangible high-altitude propulsion motor

Info

Publication number
GB1112260A
GB1112260A GB34959/66A GB3495966A GB1112260A GB 1112260 A GB1112260 A GB 1112260A GB 34959/66 A GB34959/66 A GB 34959/66A GB 3495966 A GB3495966 A GB 3495966A GB 1112260 A GB1112260 A GB 1112260A
Authority
GB
United Kingdom
Prior art keywords
charge
ignites
fragmentation
aug
releases
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
GB34959/66A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Atlantic Research Corp
Original Assignee
Atlantic Research Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Atlantic Research Corp filed Critical Atlantic Research Corp
Publication of GB1112260A publication Critical patent/GB1112260A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/36—Means for interconnecting rocket-motor and body section; Multi-stage connectors; Disconnecting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/34—Casings; Combustion chambers; Liners thereof

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

1,112,260. Self-propelled missiles. ATLANTIC RESEARCH CORPORATION. 4 Aug., 1966 [25 Aug., 1965], No. 34959/66. Heading F3A. The rocket (10), Fig. 1 (not shown), after the ejection of a payload particularly meteorological equipment with a parachute housed in section (44), is fragmented into small pieces. Burning of the propellant grain 28 ignites a gas generator 70 which expands the end of a capsule 72 to move a rod 74. This releases a timer 62 which through a cam (98). Fig. 3 (not shown), and detent (108) releases a striker (102). A primer (110) ignites a gas generator (not shown) to eject the equipment. Later a second cam (116) similarly through an igniter (122) starts booster charges 82 which ignite a primary charge 48. This charge fragments heavier parts such as a head 30. A secondary charge 50 extending the full length of the casing in the form of a layer underneath a tail fin assembly 16, is ignited sympathetically and fragments the remaining parts. Fragmentation may alternatively be initiated by radio link (162), Fig. 3 operating rod 74 through a solenoid (164). In the event of failure of the actuating means, fragmentation is initiated automatically on descent of the spent rocket, through an atmospheric pressure operated device (128), Fig. 4 (not shown). The secondary charge 50 is protected by an aluminized coating 160.
GB34959/66A 1965-08-25 1966-08-04 A frangible high-altitude propulsion motor Expired GB1112260A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US482392A US3331324A (en) 1965-08-25 1965-08-25 Frangible motor

Publications (1)

Publication Number Publication Date
GB1112260A true GB1112260A (en) 1968-05-01

Family

ID=23915882

Family Applications (1)

Application Number Title Priority Date Filing Date
GB34959/66A Expired GB1112260A (en) 1965-08-25 1966-08-04 A frangible high-altitude propulsion motor

Country Status (3)

Country Link
US (1) US3331324A (en)
DE (1) DE1506131A1 (en)
GB (1) GB1112260A (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3688988A (en) * 1970-12-14 1972-09-05 Us Army Disposable rocket motor nozzle
US4007688A (en) * 1976-02-23 1977-02-15 The United States Of America As Represented By The Secretary Of The Navy Timed missile flight termination system
DE19632597C1 (en) * 1996-08-13 1998-01-22 Daimler Benz Aerospace Ag Projectile, especially for non-lethal active components
FR2975079B1 (en) * 2011-05-13 2013-12-20 Centre Nat Etd Spatiales METHOD FOR MANUFACTURING A SPACE VEHICLE ELEMENT AND SPATIAL VEHICLE ELEMENT OBTAINED BY THE METHOD

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2937595A (en) * 1955-05-18 1960-05-24 Alco Products Inc Rocket boosters
FR1291668A (en) * 1961-03-15 1962-04-27 Development of rocket-propelled vehicles
US3185090A (en) * 1963-02-01 1965-05-25 Thiokol Chemical Corp Dual shaped charge separation system
US3135204A (en) * 1963-02-13 1964-06-02 Vincent J Menichelli Means for explosively removing the nose cone of a missile

Also Published As

Publication number Publication date
DE1506131A1 (en) 1969-06-04
US3331324A (en) 1967-07-18

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